Patents by Inventor Andreas HARTUNG

Andreas HARTUNG has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 11401621
    Abstract: A method of producing a metal strip coated with a coating, said coating containing chromium metal and chromium oxide and being electrolytically deposited from an electrolyte solution that contains a trivalent chromium compound and at least one salt for increasing conductivity and at least one acid or one base for setting a desired pH value, onto the metal strip by bringing the metal strip into electrolytically effective contact with the electrolyte solution during an electrolysis time. The metal strip is successively passed at a predefined strip travel speed in a strip travel direction through a plurality of electrolysis tanks successively arranged in the strip travel direction. At least the first electrolysis tank, as viewed in the strip travel direction, or a front group of electrolysis tanks is filled with a first electrolyte solution and the last electrolysis tank, as viewed in the strip travel direction, or a rear group of electrolysis tanks is filled with a second electrolyte solution.
    Type: Grant
    Filed: April 6, 2020
    Date of Patent: August 2, 2022
    Assignee: thyssenkrupp Rasselstein GmbH
    Inventors: Andrea Marmann, Christoph Molls, Sebastian Hartung
  • Patent number: 11215062
    Abstract: A blade arrangement for a turbomachine, in particular a gas turbine, with a first blade, which has a first blade body and a first platform, and a second blade, which is adjacent in the peripheral direction, and has a second blade body and a second platform. A first wall of the first blade and a second wall of the second blade bound a blade cavity, in which a damper with a wall-side contact surface is arranged. This contact surface has at least one first surface portion, which is convexly curved in a first direction, which, in at least one contact position, contacts the first wall in the first surface portion and is parallel to at least one portion of an edge of the first platform, said edge facing the second platform.
    Type: Grant
    Filed: December 10, 2019
    Date of Patent: January 4, 2022
    Assignee: MTU Aero Engines AG
    Inventors: Andreas Hartung, Martin Pernleitner
  • Patent number: 11149585
    Abstract: The present invention relates to a turbomachine assembly with an annular flow cascade, which has a plurality of blades, which are arranged distributed in a peripheral direction, and a detuning device for different detuning of natural frequencies of the blades, wherein the detuning device has a ring that revolves in the peripheral direction, or wherein the detuning device has all detuning elements that are arranged at the blade, which follow one another in a row in the peripheral direction, and are designed in such a way that, during operation, first blades of the flow cascade each contact at most one, in particular, no movable detuning element of the detuning device.
    Type: Grant
    Filed: May 23, 2019
    Date of Patent: October 19, 2021
    Assignee: MTU Aero Engines AG
    Inventor: Andreas Hartung
  • Patent number: 11118458
    Abstract: A combination including a seal (36-38) for sealing a gap (s) between blade platforms (11, 21) of two adjacent blades of a turbomachine and a reducer (31; 32-34) for reducing vibrations of at least one of the blades, the seal including at least one rib (36) having a rib thickness and at least one wall (37) having a wall thickness that is smaller than the rib thickness and/or the reducer including a tuning-element guide housing (32) having at least one cavity (33) in which at least one tuning element (34) is disposed with play for impacting contact with the tuning-element guide housing.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: September 14, 2021
    Assignee: MTU Aero Engines AG
    Inventor: Andreas Hartung
  • Patent number: 11002140
    Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: May 11, 2021
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Patent number: 10884255
    Abstract: Methods, devices and systems for linear polarization of a laser beam are provided. In one aspect, a polarization system includes: a first polarizer having a first polarizer surface for linear polarization of a laser beam propagating in a first direction and striking the first polarizer surface at a first angle, a phase shifter configured to rotate a polarization direction of the linearly polarized laser beam transmitted at the first polarizer surface by a predetermined rotation angle, and a second polarizer having a second polarizer surface, the linearly polarized laser beam striking the second polarizer surface at a second angle after having passed through the phase shifter and being transmitted by the second polarizer surface. An incidence plane of the laser beam striking the second polarizer surface is rotated by the predetermined rotation angle relative to an incidence plane of the laser beam striking the first polarizer surface.
    Type: Grant
    Filed: April 12, 2018
    Date of Patent: January 5, 2021
    Assignee: TRUMPF Lasersystems for Semiconductor Manufacturing GmbH
    Inventors: Guenther Krauss, Andrea Hartung
  • Publication number: 20200240277
    Abstract: The present invention relates to a blade arrangement for a turbomachine, in particular a gas turbine, with a first blade, which has a first blade body and a first platform, and a second blade, which is adjacent in the peripheral direction, and has a second blade body and a second platform, wherein a first wall of the first blade and a second wall of the second blade bound a blade cavity, in which a damper with a wall-side contact surface is arranged, wherein this contact surface has at least one first surface portion, which is convexly curved in a first direction, which, in at least one contact position, contacts the first wall in the first surface portion and is parallel to at least one portion of an edge of the first platform, said edge facing the second platform.
    Type: Application
    Filed: December 10, 2019
    Publication date: July 30, 2020
    Applicant: MTU Aero Engines AG
    Inventors: Andreas Hartung, Martin Pernleitner
  • Patent number: 10689983
    Abstract: An impulse body module a turbine stage of a gas turbine includes a holder component of one-piece construction, with a base and surrounding side walls arranged at the base, wherein the side walls and the base define a holding chamber; an insert component, of one-piece construction, which is inserted into the holding chamber of the holder component, wherein the holder component and the insert component accommodated therein define a number of mutually separated cavities, and wherein an impulse body, in particular a sphere, is accommodated in each cavity; and a closure component of one-piece construction, which is joined to the holder component in a material-bonded manner where the holding chamber is closed and the insert component is surrounded by the holder component and the closure component. The holder component has at least one base projection in the region of its base, which extends away from the holding chamber.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: June 23, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Gerhard-Heinz Roesele, Martin Pernleitner, Manfred Schill, Manfred Feldmann, Adrian Ehrenberg
  • Patent number: 10570752
    Abstract: An impulse element module for a turbomachine, in particular a turbine stage of a gas turbine, preferably an aircraft gas turbine, including a single-unit receptacle component having a base and side walls that extend peripherally thereon, the side walls and the base bounding a receiving space; a single-unit insert component having a form that is inserted into receiving space of receptacle component; together, the receptacle component and the insert component accommodated therein being designed to define a plurality of spaced apart cavities; and an impulse element, in particular a sphere, being accommodated in each cavity; and a single-unit sealing component that is joined in a material-to-material bond to the receptacle component in a way that allows the receiving space to be sealed and the insert component to be surrounded by the receptacle component and the sealing component.
    Type: Grant
    Filed: May 5, 2017
    Date of Patent: February 25, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Gerhard-Heinz Roesele, Markus Schlemmer, Andreas Hartung
  • Patent number: 10550720
    Abstract: A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: February 4, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Patent number: 10526896
    Abstract: The present invention relates to a turbomachine blade or vane arrangement having a first turbomachine blade or vane, a second turbomachine blade or vane adjacent to it, and at least one tuning element guide housing with at least one cavity, in which at least one tuning element is arranged with play of movement for impact contact with the tuning element guide housing, with the tuning element guide housing being arranged at least in part in a recess, in particular in a frame, of the first turbomachine blade or vane, where the second turbomachine blade or vane has at least one first rib for securing the tuning element guide housing arranged in the recess.
    Type: Grant
    Filed: April 17, 2017
    Date of Patent: January 7, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Andreas Hartung, Manfred Schill
  • Patent number: 10526901
    Abstract: A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).
    Type: Grant
    Filed: March 14, 2017
    Date of Patent: January 7, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Gerhard-Heinz Roesele, Andreas Hartung
  • Publication number: 20190360354
    Abstract: The present invention relates to a turbomachine assembly with an annular flow cascade, which has a plurality of blades, which are arranged distributed in a peripheral direction, and a detuning device for different detuning of natural frequencies of the blades, wherein the detuning device has a ring that revolves in the peripheral direction, or wherein the detuning device has all detuning elements that are arranged at the blade, which follow one another in a row in the peripheral direction, and are designed in such a way that, during operation, first blades of the flow cascade each contact at most one, in particular, no movable detuning element of the detuning device.
    Type: Application
    Filed: May 23, 2019
    Publication date: November 28, 2019
    Applicant: MTU Aero Engines AG
    Inventor: Andreas Hartung
  • Patent number: 10451089
    Abstract: A blade for a turbomachine, in particular a compressor or turbine stage of a gas turbine, having at least one matrix having a first impact chamber (10) in which at least one impulse element (11) is disposed with play, at least one second impact chamber (20) whose volumetric centroid is offset from a volumetric centroid of the first impact chamber (10) along a first matrix axis (A) and in which at least one impulse element (21) is disposed with play, and at least one third impact chamber (30) whose volumetric centroid is offset from the volumetric centroid of the first impact chamber (10) along a second matrix axis (B) transversely to the first matrix axis (A) and in which at least one impulse element (31) is disposed with play, the first matrix axis (A) and an axis of rotation (R) of the turbomachine forming an angle of at least 60° and no more than 120° is provided.
    Type: Grant
    Filed: September 6, 2016
    Date of Patent: October 22, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder, Manfred Schill
  • Patent number: 10422231
    Abstract: The present invention relates to a bladed rotor for a gas turbine, with a body and a plurality of rotating blades where contact regions of a cylindrical surface of the body and front faces of the rotating blades are joined together cohesively. At least one of these contact regions and/or at least one of these front faces has at least one blind hole, in which at least one impulse body is arranged with play of movement and which is sealed and rotating blades are joined with the cylindrical surface. Alternatively, the body and rotating blades are manufactured integrally with one another by machining, and at least one blind hole extends from an inner surface of the body facing away from the blade out to one of the rotating blades, at least one impulse body being disposed with play of movement in this hole, and this hole is sealed.
    Type: Grant
    Filed: August 8, 2016
    Date of Patent: September 24, 2019
    Assignee: MTU Aero Engines AG
    Inventor: Andreas Hartung
  • Patent number: 10415425
    Abstract: The invention relates to a turbomachine including: a guide baffle, whose sv guide blades are situated on c guide blade carriers; and an adjacent moving baffle including sb moving blades; the guide baffle nv including impulse bodies which are situated in a cavity system of the guide baffle with movement play with respect to the impulse contact; the moving baffle nb including impulse bodies which are situated in a cavity system of the moving baffle with movement play with respect to the impulse contact; and quotient ? i = 1 n v ? ? m i s v - c of sum ? i = 1 n v ? ? m i of the masses of all impulse bodies of the guide baffle divided by the difference (sv?c) of the number sv of all guide blades minus the number c of all guide blade carriers amounts to at least 1.
    Type: Grant
    Filed: January 17, 2017
    Date of Patent: September 17, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Andreas Hartung, Karl-Hermann Richter, Herbert Hanrieder
  • Patent number: 10287910
    Abstract: The present invention relates to an adjustable guide vane for a turbomachine, having a vane element and a turning disk, which has a first impact chamber, in which an impulse element is arranged with play of movement.
    Type: Grant
    Filed: January 11, 2016
    Date of Patent: May 14, 2019
    Assignee: MTU Aero Engines AG
    Inventor: Andreas Hartung
  • Publication number: 20190128120
    Abstract: A combination including a seal (36-38) for sealing a gap (s) between blade platforms (11, 21) of two adjacent blades of a turbomachine and a reducer (31; 32-34) for reducing vibrations of at least one of the blades, the seal including at least one rib (36) having a rib thickness and at least one wall (37) having a wall thickness that is smaller than the rib thickness and/or the reducer including a tuning-element guide housing (32) having at least one cavity (33) in which at least one tuning element (34) is disposed with play for impacting contact with the tuning-element guide housing.
    Type: Application
    Filed: October 22, 2018
    Publication date: May 2, 2019
    Inventor: Andreas HARTUNG
  • Patent number: 10247005
    Abstract: A blade or vane arrangement for a turbomachine includes a turbomachine blade or vane and at least one tuning element guide housing with at least one cavity, in which at least one tuning element, which is provided for impact contact with the tuning element guide housing is taken up, the tuning element guide housing being arranged in a recess of the turbomachine blade or vane, wherein the cavity of the tuning element guide housing in which the tuning element is taken up, is closed in a gas-tight manner.
    Type: Grant
    Filed: November 6, 2015
    Date of Patent: April 2, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Andreas Hartung, Manfred Schill, Gerhard-Heinz Roesele
  • Patent number: 10155196
    Abstract: A catalytic converter reactor having in-built catalytic converter modules, wherein the total flow impingement surface area provided by the catalytic converter elements fitted in the catalytic converter modules is larger than the flow impingement surface area of the catalytic converter reactor, the module impingement surface area being defined by the catalytic converter module surfaces facing the main flow direction, and the catalytic converter modules being positioned so that the waste gas flows through the catalytic converter elements contained therein in a direction different from the flow direction on the intake and exit sides.
    Type: Grant
    Filed: June 20, 2014
    Date of Patent: December 18, 2018
    Assignee: IBIDEN PORZELLANFABRIK FRAUENTHAL GMBH
    Inventors: Kurt Orehovsky, Michael Aumann, Andreas Hartung, Thomas Krainer, Thomas Nagl, Gerhard Poelzl, Mario Schweiger